Variable geometry inlet system

1. An aeroengine comprising:

a compressor section having an axis;

a combustion section;

a turbine section; and

a nacelle surrounding at least the compressor section, the nacelle including:

a main portion in a stationary relationship with the compressor section, the main portion having an annular outer skin and an inner barrel radially spaced apart from each other, the inner barrel having a front section extending forward out of a front edge of the annular outer skin,

an inlet cowl having an annular outer skin, an annular inner wall radially spaced apart from the annular outer skin, and a lip portion extending radially between, and connected with, the annular outer skin and the annular inner wall, the annular outer skin and the annular inner wall defining an annular space therebetween, the annular space having an open ended aft end, the inlet cowl disposed upstream of the main portion with respect to an air flow entering the nacelle through a front opening circumscribed by the lip portion of the inlet cowl, the inlet cowl translatable relative to the main portion of the nacelle between a retracted position in which the annular outer skin of the inlet cowl and the annular outer skin of the main portion of the nacelle are immediately axially adjacent each other and in which the front section of the inner barrel is received within the annular space between the annular outer skin and the annular inner wall of the inlet cowl by a first axial extent of insertion, and an extended position in which the annular outer skin of the inlet cowl projects to a location further upstream than the annular outer skin of the main portion of the nacelle, and in which the front section of the inner barrel of the main portion is received within the annular space between the annular outer skin and the annular inner wall of the inlet cowl by a second axial extent of insertion that is less than the first axial extent of insertion, the annular inner wall of the inlet cowl and the inner barrel of the main portion thereby forming a length-variable inlet duct for directing the air flow toward the compressor section.

2. The aeroengine defined in claim 1 wherein the front section of the inner barrel is operatively connected to the inner wall of the inlet cowl in a telescoping configuration, the annular inner skin of the lip portion of the inlet cowl spaced radially inwardly from the front section of the inner barrel when the inlet cowl is in the retracted position.

3. The aeroengine defined in claim 2 wherein the inner wall and the inner barrel each comprise a respective inner surface in combination defining a variable-geometry acoustic treatment area.

4. The aeroengine defined in claim 1 , wherein the lip portion of the inlet cowl defines the front opening in both the extended and the retracted positions.

5. A variable geometry inlet system of an aeroengine comprising:

an inlet duct for directing an air flow from a front opening in the inlet duct to a compressor, the inlet duct having:

an annular lip circumscribing the front opening,

a first section, and

a second section movable relative to the first section between an extended position and a retracted position, the first and second sections in the extended position defining an axially longer inlet duct than when in the retracted position, the inlet duct extending continuously from the front opening to the compressor in both positions and providing only one inlet path for the air flow from the front opening to the compressor regardless of the inlet duct position, the front opening of the inlet duct having a same diameter in the extended position and the retracted position,

wherein the first section has an annular outer skin and an inner barrel with a front section of the inner barrel extending further forward than a front edge of the annular outer skin, and

wherein the second section has the annular lip extending radially between, and connected with, an annular outer skin and an annular inner wall to define an annular space having an open ended aft end, the front section of the inner barrel axially received in the annular space of the second section when the second section is in the retracted position and when the second section is in the extended position.

6. The variable geometry inlet system as defined in claim 5 , wherein the first and second sections each include an acoustic treatment area respectively defined on the inner wall of the second section and an inner surface of the front section of the inner barrel of the first section to form a variable-geometry acoustic treatment area, and wherein in the extended position the acoustic treatment area defined by the inner surface of the front section of the inner barrel of the first section is exposed and a total acoustic treatment area of the variable-geometry acoustic treatment area is increased with respect to the total acoustic treatment area of the variable-geometry acoustic treatment area in the retracted position.

7. The variable geometry inlet system defined in claim 5 , wherein the annular lip is provided at a forward end of the second section, and wherein the annular lip defines the front opening in both the extended and the retracted positions.